Light weight swirler for gas turbine engine combustor and a method for lightening a swirler for a gas turbine engine

ABSTRACT

The disclosure is directed to a swirler body for a combustor of a gas turbine engine, where the swirler body includes an annular mount face which defines at least one pocket. The disclosure is directed to a swirler assembly for a combustor of a gas turbine engine, where the swirler assembly includes a swirler first body with an annular first mount face which defines at least one first pocket and a swirler second body with an annular second mount face which abuts said annular first mount face, where said second annular mount face defines at least one second pocket. The disclosure is directed to a method of lightening a swirler assembly for a combustor of a gas turbine engine, where the method includes defining at least one pocket within an annular mount face of a swirler body.

This application is a continuation of U.S. patent application Ser. No.13/614,657 filed Sep. 13, 2012, the contents of which are incorporatedherein by reference.

BACKGROUND

The present disclosure relates to a gas turbine engine and, moreparticularly, to a swirler therefor.

Gas turbine engines, such as those that power modem commercial andmilitary aircraft, include a compressor to pressurize airflow, acombustor to burn a hydrocarbon fuel in the presence of the pressurizedairflow, and a turbine to extract energy from the resultant combustiongases.

The combustor generally includes radially spaced inner and outer linersthat define an annular combustion chamber therebetween. Arrays ofcircumferentially distributed combustion air holes penetrate multipleaxial locations along each liner to radially admit the pressurized airinto the combustion chamber. A plurality of circumferentiallydistributed fuel nozzles project into a forward section of thecombustion chamber through a respective fuel nozzle swirler to supplythe fuel to be mixed with the pressurized air.

SUMMARY

A swirler body for a combustor of a gas turbine engine according to onedisclosed non-limiting embodiment of the present disclosure includes anannular mount face which defines at least one pocket.

In a further embodiment of the foregoing embodiment, the swirler bodyincludes a first slot and a second slot which are generally radial withrespect to a centerline of said swirler body, the at least one pocketbetween the first slot and the second slot.

In a further embodiment of any of the foregoing embodiments, the atleast one pocket extends through an outer surface of the swirler body.

A swirler assembly for a combustor of a gas turbine engine according toanother disclosed non-limiting embodiment of the present disclosureincludes a swirler first body with an annular first mount face whichdefines at least one first pocket, and a swirler second body with asecond annular mount face which abuts the annular first mount face, thesecond annular mount face defines at least one second pocket.

In a further embodiment of any of the foregoing embodiments, the swirlerfirst body includes a first slot and a second slot which are generallyradial with respect to a centerline of said swirler first body, the atleast one pocket between the first slot and the second slot. In thealternative or additionally thereto, the swirler second body includes afirst slot and a second slot which are generally radial with respect toa centerline of said swirler second body, the at least one pocketbetween the first slot and the second slot.

In the alternative or additionally thereto, the outer surface iscylindrical.

In a further embodiment of any of the foregoing embodiments, a guidehousing is mounted to the swirler first body.

In the alternative or additionally thereto, the nozzle guide is mountedto the guide housing.

In the alternative or additionally thereto, a capture plate is mountedto the guide housing to retain the nozzle guide, the nozzle guidemovable with respect to the guide housing.

In the alternative or additionally thereto, a capture plate is mountedto the guide housing to retain the nozzle guide.

In the alternative or additionally thereto, the capture plate isannular.

In the alternative or additionally thereto, the capture plate includes anon-circular inner periphery.

In the alternative or additionally thereto, the capture plate includes ascalloped inner periphery.

A method of lightening a swirler assembly for a combustor of a gasturbine engine according to another disclosed non-limiting embodiment ofthe present disclosure includes at least one pocket within an annularmount face of a swirler body.

In a further embodiment of the foregoing embodiment, the method includesdefining at least one pocket completely within the annular mount face.

In a further embodiment of any of the foregoing embodiments, the methodincludes defining at least one pocket adjacent to a slot.

In a further embodiment of any of the foregoing embodiments, the methodincludes at least one pocket through an outer surface of the swirlerbody.

In a further embodiment of any of the foregoing embodiments, the methodincludes defining at least one pocket adjacent to a second pocket in aswirler second body.

BRIEF DESCRIPTION OF THE DRAWINGS

Various features will become apparent to those skilled in the art fromthe following detailed description of the disclosed non-limitingembodiment. The drawings that accompany the detailed description can bebriefly described as follows:

FIG. 1 is a schematic cross-section of a gas turbine engine;

FIG. 2 is a partial sectional view of an exemplary annular combustorthat may be used with the gas turbine engine shown in FIG. 1;

FIG. 3 is an exploded view of a swirler assembly according to onenon-limiting embodiment;

FIG. 4 is an expanded view of a swirler first body;

FIG. 5 is a partial sectional view of the swirler assembly of FIG. 3;

FIG. 6 is an expanded view of a swirler second body;

FIG. 7 is an expanded partial sectional view of the swirler assembly ofFIG. 3;

FIG. 8 is an end view of the swirler assembly of FIG. 3;

FIG. 9 is an exploded view of a swirler assembly according to anothernon-limiting embodiment; and

FIG. 10 is an expanded perspective view of the swirler assembly of FIG.9.

FIGS. 11A-11B illustrate an exploded view of a swirler assemblyaccording to another non-limiting embodiment.

DETAILED DESCRIPTION

FIG. 1 schematically illustrates a gas turbine engine 20. The gasturbine engine 20 is disclosed herein as a two-spool turbofan thatgenerally incorporates a fan section 22, a compressor section 24, acombustor section 26 and a turbine section 28. Alternative engines mightinclude an augmentor section (not shown) among other systems orfeatures. The fan section 22 drives air along a bypass flowpath whilethe compressor section 24 drives air along a core flowpath forcompression and communication into the combustor section 26 thenexpansion through the turbine section 28. Although depicted as aturbofan gas turbine engine in the disclosed non-limiting embodiment, itshould be understood that the concepts described herein are not limitedto use with turbofans as the teachings may be applied to other types ofturbine engines such as a three-spool (plus fan) engine wherein anintermediate spool includes an intermediate pressure compressor (IPC)between the LPC and HPC and an intermediate pressure turbine (IPT)between the HPT and LPT.

The engine 20 generally includes a low spool 30 and a high spool 32mounted for rotation about an engine central longitudinal axis Arelative to an engine static structure 36 via several bearing structures38. The low spool 30 generally includes an inner shaft 40 thatinterconnects a fan 42, a low pressure compressor 44 (“LPC”) and a lowpressure turbine 46 (“LPT”). The inner shaft 40 drives the fan 42directly or through a geared architecture 48 to drive the fan 42 at alower speed than the low spool 30. An exemplary reduction transmissionis an epicyclic transmission, namely a planetary or star gear system.

The high spool 32 includes an outer shaft 50 that interconnects a highpressure compressor 52 (“HPC”) and high pressure turbine 54 (“HPT”). Acombustor 56 is arranged between the high pressure compressor 52 and thehigh pressure turbine 54. The inner shaft 40 and the outer shaft 50 areconcentric and rotate about the engine central longitudinal axis A whichis collinear with their longitudinal axes.

Core airflow is compressed by the low pressure compressor 44 then thehigh pressure compressor 52, mixed with the fuel and burned in thecombustor 56, then expanded over the high pressure turbine 54 and lowpressure turbine 46. The turbines 54, 46 rotationally drive therespective low spool 30 and high spool 32 in response to the expansion.

The main engine shafts 40, 50 are supported at a plurality of points bybearing structures 38 within the static structure 36. It should beunderstood that various bearing structures 38 at various locations mayalternatively or additionally be provided.

With reference to FIG. 2, the combustor 56 generally includes acombustor outer wall 60 and a combustor inner wall 62. The outer wall 60and the inner wall 62 are spaced inward from a diffuser case 64 suchthat a chamber 66 is defined therebetween. The chamber 66 is generallyannular in shape and is defined between combustor walls 60, 62.

The outer wall 60 and the diffuser case 64 define an annular outerplenum 76 and the inner wall 62 and the diffuser case 64 define anannular inner plenum 78. It should be understood that although aparticular combustor is illustrated, other combustor types with variouscombustor liner arrangements will also benefit herefrom. It should befurther understood that the disclosed cooling flow paths are but anillustrated embodiment and should not be limited only thereto.

Each wall 60, 62 generally includes a respective support shell 68, 70that supports one or more respective liners 72, 74 mounted to a hot sideof the respective support shell 68, 70. The liners 72, 74 define a linerarray that may be generally annular in shape. Each of the liners 72, 74may be generally rectilinear and manufactured of, for example, a nickelbased super alloy or ceramic material.

The combustor 56 further includes a forward assembly 80 immediatelydownstream of the compressor section 24 to receive compressed airflowtherefrom. The forward assembly 80 generally includes an annular hood82, a bulkhead subassembly 84, a multiple of fuel nozzles 86 (one shown)and a multiple of swirlers 90 (one shown) that defines a central opening92. The annular hood 82 extends radially between, and is secured to, theforwardmost ends of the walls 60, 62. The annular hood 82 includes amultiple of circumferentially distributed hood ports 94 that accommodatethe respective fuel nozzle 86 and introduce air into the forward end ofthe chamber 66. The centerline of the fuel nozzle 86 is concurrent withthe centerline F of the respective swirler 90. Each fuel nozzle 86 maybe secured to the diffuser case 64 to project through one of the hoodports 94 and through the central opening 92 within the respectiveswirler 90.

Each swirler 90 is circumferentially aligned with one of the hood ports94 to project through the bulkhead subassembly 84. Each bulkheadsubassembly 84 includes a bulkhead support shell 96 secured to the walls60, 62, and a multiple of circumferentially distributed bulkheadheatshields 98 secured to the bulkhead support shell 96 around thecentral opening 92.

The forward assembly 80 directs a portion of the core airflow into theforward end of the chamber 66 while the remainder enters the annularouter plenum 76 and the annular inner plenum 78. The multiple of fuelnozzles 86, swirler 90 and surrounding structure generate a swirling,intimately blended fuel-air mixture that supports combustion in thechamber 66.

With reference to FIG. 3, each of the swirlers 90 generally includes acapture plate 100, a nozzle guide 102, a guide housing 104, a swirlerfirst body 106 and a swirler second body 108. The capture plate 100 ismounted to the guide housing 104 to retain the nozzle guide 102, thenozzle guide 102 is movable with respect to the guide housing 104. Itshould be appreciated that any number of swirler bodies as well asalternative or additional components may be utilized herewith and thatthe two part swirler body shown is merely but one example assembly.

With reference to FIG. 4, the swirler first body 106 generally includesa base section 110 and a frustoconical section 112 which extendsdownstream of the base section 110. The base section 110 includes amultiple of legs 114 defined by a multiple of slots 116 opposite thefrustoconical section 112. The slots 116 are generally radial withrespect to the centerline F to receive primary combustion core airflowfrom within the bulkhead support shell 96 toward the fuel nozzle 86within the chamber 66 for combustion (FIG. 5). It should be appreciatedthat generally radial as defined herein means transverse to saidcenterline F but may include an angled component to impart a swirl tothe primary combustion core airflow about the centerline F.

A multiple of pockets 118 are formed in and communicate axially throughthe base section 110 opposite the legs 114. The multiple of pockets 118in the disclosed non-limiting embodiment are completely contained withina mount face 120 which abuts the swirler second body 108 (FIG. 5).

With reference to FIG. 6, the swirler second body 108 generally includesa base section 122 and a frustoconical section 124 which extendsdownstream of the base section 122. The base section 122 includes amultiple of slots 126 and a multiple of pockets 128 in a mount face 130of the swirler second body 108. The multiple of slots 126 are generallyradial with respect to the centerline F to receive primary combustioncore airflow to be communicated toward the chamber 66 for combustionfrom within the bulkhead support shell 96 toward the fuel nozzle 86. Themultiple of slots 126 may provide counter swirl with respect to slots116 (FIG. 4).

The mount face 130 of the swirler second body 108 abuts the mount face120 of the swirler first body 106 such that the pockets 118, 128 may bein axial association but are not exposed to the primary combustion coreairflow (FIG. 7). That is, the pockets 118, 128 form respective singlehollow areas contained within the mount faces 120, 130.

The base section 122 at least partially overlaps the base section 110 toseal as well as rotationally locate the swirler first and second bodies106, 108. That is, a lip of the base section 122 may at least partiallysurround the base section 110.

The pockets 118, 128 thereby reduce the weight of the swirler 90. Itshould be appreciated that the pockets 118, 128 may be machined orotherwise framed into a cast component or formed directly through, forexample only, Direct Laser Metal Sintering (DLMS).

With reference to FIG. 8, the capture plate 100 may also be lightenedthrough formation of a scalloped inner aperture 100A. It should beappreciated that the scalloping is but one disclosed non-limitingembodiment and various geometries for the inner aperture may be providedsuch as rectilinear, oval or other non-circular shapes. In the disclosednon-limiting embodiment, each swirler 90 has been lightened byapproximately 0.04 pounds (18 grams) which, for example only, in acombustor with eighteen swirlers provides a 0.7 pound (317 gram) weightsavings.

With reference to FIGS. 11A-11B, in another disclosed, non-limitingembodiment, a swirler 90″ includes a swirler second body 108′ in whichthe pockets 128′ extend through an outer surface 132 such that primarycombustion core airflow may enter the pockets 128′ and pockets 118 butis trapped therein. That is, the primary combustion core airflow mayimpinge within the pockets 128′, 118 but is not swirled nor communicatedtoward the combustion chamber 66 for combustion.

Referring to FIG. 9 (swirler 90′) and FIGS. 11A-11B, in some embodimentsthe pockets 128′ are located between each of the multiple of slots 126′such that relatively thin legs 134 are defined, each of which includesone of the multiple of slots 126′ which communicate primary combustioncore airflow toward the combustion chamber 66 for combustion. At leastone of the multiple of legs 134A may be of an extended length to bereceived within a corresponding axial recess 136 in the swirler firstbody 106′ to assure the swirler first body 106′ is properly clockedrelative to the swirler second body 108′ (FIG. 10). In other words, thepockets 118, 128 are aligned in some manner so as to be sealed off fromthe primary airflow through the swirler. The pockets 118, 128 do notnecessarily have to be aligned one to another so long as there is nointeraction with the primary airflow. The clocking feature providesalignment to ensure the swirler first body 106′ is properly clockedrelative to the swirler second body 108′ and can't be misaligned duringan assembly process. It should be understood that relative positionalterms such as “forward,” “aft,” “upper,” “lower,” “above,” “below,” andthe like are with reference to the normal operational attitude of thevehicle and should not be considered otherwise limiting.

It should be understood that like reference numerals identifycorresponding or similar elements throughout the several drawings. Itshould also be understood that although a particular componentarrangement is disclosed in the illustrated embodiment, otherarrangements will benefit herefrom.

Although particular step sequences are shown, described, and claimed, itshould be understood that steps may be performed in any order, separatedor combined unless otherwise indicated and will still benefit from thepresent disclosure.

The foregoing description is exemplary rather than defined by thelimitations within. Various non-limiting embodiments are disclosedherein, however, one of ordinary skill in the art would recognize thatvarious modifications and variations in light of the above teachingswill fall within the scope of the appended claims. It is therefore to beunderstood that within the scope of the appended claims, the disclosuremay be practiced other than as specifically described. For that reasonthe appended claims should be studied to determine true scope andcontent.

What is claimed is:
 1. A method of lightening a swirler assembly for acombustor of a gas turbine engine, the method comprising: defining atleast one first pocket within an annular first mount face of a firstswirler body; abutting the annular first mount face of the first swirlerbody with an annular second mount face of a second swirler body suchthat the at least one first pocket of the annular first mount face andat least one second pocket of the annular second mount face areconfigured to receive a primary combustion core airflow such that theprimary combustion core airflow enters the at least one first pocket andthe at least one second pocket and is trapped therein and impingeswithin the at least one first pocket and the at least one second pocketbut is not swirled or communicated toward a combustion chamber, anddefining said at least one first pocket adjacent to a slot.
 2. Themethod as recited in claim 1, further comprising: defining a captureplate that retains a nozzle guide.
 3. The method as recited in claim 1,further comprising: extending said at least one first pocket through anouter surface of said first swirler body.
 4. A swirler assembly for acombustor of a gas turbine engine comprising: a swirler first body withan annular first mount face which defines at least one first pocket; anda swirler second body with an annular second mount face that defines atleast one second pocket and which abuts said annular first mount facesuch that the at least one first pocket and the at least one secondpocket are configured to receive a primary combustion core airflow suchthat the primary combustion core airflow enters the at least one firstpocket and the at least one second pocket and is trapped therein andimpinges within the at least one first pocket and the at least onesecond pocket but is not swirled or communicated toward a combustionchamber, wherein said swirler first body includes a first slot and asecond slot which each extend substantially radially with respect to acenterline of said swirler first body, said at least one first pocketdisposed between said first slot and said second slot, wherein saidswirler second body includes a third slot and a fourth slot which eachextend substantially radially with respect to a second centerline ofsaid swirler second body, said at least one second pocket disposedbetween said third slot and said fourth slot.
 5. The swirler assembly asrecited in claim 4, wherein said at least one first pocket and said atleast one second pocket are in axial alignment.
 6. The swirler assemblyas recited in claim 4, wherein said at least one first pocket extendsthrough an outer surface of said swirler first body.
 7. The swirlerassembly as recited in claim 4, wherein said at least one second pocketcommunicates through an outer surface of said swirler second body. 8.The swirler assembly as recited in claim 7, wherein said outer surfaceis cylindrical.
 9. The swirler assembly as recited in claim 4, furthercomprising a guide housing mounted to said swirler first body.
 10. Theswirler assembly as recited in claim 9, wherein a nozzle guide ismounted to said guide housing.
 11. The swirler assembly as recited inclaim 10, wherein a capture plate is mounted to said guide housing toretain said nozzle guide, said nozzle guide being movable with respectto said guide housing.
 12. The swirler assembly as recited in claim 10,wherein a capture plate is mounted to said guide housing to retain saidnozzle guide.
 13. The swirler assembly as recited in claim 12, whereinsaid capture plate is annular.
 14. The swirler assembly as recited inclaim 13, wherein said capture plate includes a scalloped innerperiphery.